Airworthiness Directives; Airbus Airplanes, 21858-21860 [2018-09848]

Download as PDF 21858 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations (2) Bombardier Service Bulletin 700–71– 003, dated December 5, 2016 (for Bombardier Model BD–700–1A10 airplanes). (3) Bombardier Service Bulletin 700–71– 5003, dated December 5, 2016 (for Bombardier Model BD–700–1A11 airplanes). (4) Bombardier Service Bulletin 700–71– 6003, dated December 5, 2016 (for Bombardier Model BD–700–1A10 airplanes). (k) New Requirement of This AD: Nut and Bolt Replacements, and Gap Measurement Within 1,000 flight hours or 12 months, whichever occurs first after the effective date of this AD: Replace the nuts having part number (P/N) AS54365 and the bolts having P/N AS54020 and AS54002 in the engine rear mount assembly with new nuts and new bolts; and do the gap measurement to determine if the gap is within acceptable limits; in accordance with Part B of the Accomplishment Instructions of the applicable service information specified in paragraphs (j)(1) through (j)(4) of this AD. (l) New Requirement of This AD: Corrective Action If any gap is detected, during any measurement required by paragraph (j) or (k) of this AD, that is not within the applicable limits specified in the service information specified in paragraphs (j)(1) through (j)(4) of this AD, before further flight repair using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (m) No Reporting Required Although the service information identified in paragraphs (j)(1) through (j)(4) of this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. sradovich on DSK3GMQ082PROD with RULES (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before January 3, 2017 (the effective date of AD 2016–25–18), in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (n)(1) through (n)(4) of this AD. (1) Bombardier Service Bulletin 700– 1A11–71–002, dated May 31, 2016 (for Bombardier Model BD–700–1A11 airplanes). (2) Bombardier Service Bulletin 700–71– 002, dated May 31, 2016 (for Bombardier Model BD–700–1A10 airplanes). (3) Bombardier Service Bulletin 700–71– 5002, dated May 31, 2016 (for Bombardier Model BD–700–1A11 airplanes). (4) Bombardier Service Bulletin 700–71– 6002, dated May 31, 2016 (for Bombardier Model BD–700–1A10 airplanes). (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, FAA, New York ACO Branch, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7300; fax: 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2016–23R1, dated February 20, 2017, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2017–0775. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7329; fax: 516–794– 5531. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(5) and (q)(6) of this AD. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on June 15, 2018. (i) Bombardier Service Bulletin 700–1A11– 71–003, dated December 5, 2016. (ii) Bombardier Service Bulletin 700–71– 003, dated December 5, 2016. (iii) Bombardier Service Bulletin 700–71– 5003, dated December 5, 2016. (iv) Bombardier Service Bulletin 700–71– 6003, dated December 5, 2016. (4) The following service information was approved for IBR on January 3, 2017 (81 FR 90961, December 16, 2016). (i) Bombardier Service Bulletin 700–1A11– 71–002, Revision 01, dated June 30, 2016. (ii) Bombardier Service Bulletin 700–71– 002, Revision 01, dated June 30, 2016. (iii) Bombardier Service Bulletin 700–71– 5002, Revision 01, dated June 30, 2016. (iv) Bombardier Service Bulletin 700–71– 6002, Revision 01, dated June 30, 2016. (5) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote- PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 ´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone: 514–855–5000; fax: 514– 855–7401; email: thd.crj@ aero.bombardier.com; internet: https:// www.bombardier.com. (6) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09734 Filed 5–10–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0363; Product Identifier 2017–NM–108–AD; Amendment 39–19268; AD 2018–09–11] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–301, –321, –322, –341, and –342 airplanes; Model A340– 200 series airplanes; and Model A340– 300 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports of cracks on both left-hand (LH) and right-hand (RH) sides on certain frame (FR) locations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 29, 2018. We must receive comments on this AD by June 25, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0363; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206–231–3229. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2011– 0171R1, dated January 11, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–301, –321, –322, –341, and –342 airplanes; Model A340–200 series airplanes; and Model A340–300 series airplanes. The MCAI states: Fatigue damage has been found on the A330/A340 full scale fatigue test specimen in the FR40-to-fuselage skin panel junction. Corrective actions consisted of the following actions: —in-service installation of an internal reinforcing strap on related junction required by DGAC France AD 1999–448–126(B) and AD 2001–070(B), —retrofit improvement of internal reinforcing strap fatigue life through recommended Airbus SB A330–53–3145, and —new design in production through Airbus modification 44360. Recently, during embodiment of a FR40 web repair on an A330 aeroplane and during FR40 keel beam fitting replacement on an A340 aeroplane, this internal strap was removed and rototest inspection was performed on several holes. Cracks were found on both left-hand (LH) and right-hand (RH) sides on internal strap, or butt strap, or keel beam fitting, or forward fitting FR40 flange. This condition, if not detected and corrected, could lead to crack propagation, possibly resulting in reduced structural integrity of the fuselage. For the reasons described above, this [EASA] AD requires repetitive High Frequency Eddy Current (HFEC) rototest inspections on the affected adjacent holes on both LH and RH sides between stringer 38 and 39 at the FR40-to-fuselage panel junction, and in case of crack finding, accomplishment of the associated corrective actions. * * * * * You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0363. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the 21859 MCAI. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason(s) stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0363; Product Identifier 2017–NM–108–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance Currently, there are no affected U.S.registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, we provide the following cost estimates to comply with this AD: ESTIMATED COSTS Labor cost Repetitive special detailed inspection ............ sradovich on DSK3GMQ082PROD with RULES Action 54 work-hours × $85 per hour = $4,590 per inspection cycle. We estimate the following costs to do any necessary on-condition repair that VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 Parts cost Cost per product $0 $4,590 per inspection cycle. would be required based on the results of the required actions: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 21860 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Rules and Regulations ON-CONDITION COSTS Action Labor cost Parts cost Repair ...................................................... 9 work-hours × $85 per hour = $765 ..... Up to $3,200 .......................................... sradovich on DSK3GMQ082PROD with RULES Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. VerDate Sep<11>2014 22:27 May 10, 2018 Jkt 244001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2018–09–11 Airbus: Amendment 39–19268; Docket No. FAA–2018–0363; Product Identifier 2017–NM–108–AD. (a) Effective Date This AD becomes effective May 29, 2018. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, on which Airbus modification 44360 has not been embodied in production. (1) Airbus Model A330–301, –321, –322, –341, and –342 airplanes, all manufacturer serial numbers on which Airbus Service Bulletin A330–53–3093 has been embodied in service, except those on which Airbus Service Bulletin A330–53–3145 has been embodied in service. (2) Airbus Model A340–211, –212, –213 airplanes, all manufacturer serial numbers on which Airbus Service Bulletin A340–53– 4104 has been embodied in service. (3) Airbus Model A340–311, –312, and –313 airplanes, all manufacturer serial numbers on which Airbus Service Bulletin A340–53–4104 has been embodied in service. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks on both left-hand (LH) and right-hand (RH) sides on certain frame (FR) 40 locations. We are issuing this AD to detect and correct cracks of the fuselage panel junction fasteners at FR40 on both LH and RH sides. Such a condition could lead to crack PO 00000 Frm 00020 Fmt 4700 Sfmt 9990 Cost per product Up to $3,965. propagation, possibly resulting in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Action(s) Within 30 days after the effective date of this AD, request instructions from the Manager, International Section, Transport Standards Branch, FAA, to address the unsafe condition specified in paragraph (e) of this AD; and accomplish the actions at the times specified in, and in accordance with, those instructions. Guidance can be found in Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) AD 2011–0171R1, dated January 11, 2013. (h) Alternative Methods of Compliance (AMOCs) The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (i)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (i) Related Information (1) Refer to MCAI EASA AD 2011–0171R1, dated January 11, 2013, for related information. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0363. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206–231–3229. (j) Material Incorporated by Reference None. Issued in Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09848 Filed 5–10–18; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\11MYR1.SGM 11MYR1

Agencies

[Federal Register Volume 83, Number 92 (Friday, May 11, 2018)]
[Rules and Regulations]
[Pages 21858-21860]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09848]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0363; Product Identifier 2017-NM-108-AD; Amendment 
39-19268; AD 2018-09-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-301, -321, -322, -341, and -342 airplanes; Model 
A340-200 series airplanes; and Model A340-300 series airplanes. This AD 
requires contacting the FAA to obtain instructions for addressing the 
unsafe condition on these products, and doing the actions specified in 
those instructions. This AD was prompted by reports of cracks on both 
left-hand (LH) and right-hand (RH) sides on certain frame (FR) 
locations. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD becomes effective May 29, 2018.
    We must receive comments on this AD by June 25, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 21859]]

     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0363; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone: 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2011-0171R1, dated January 11, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A330-301, -321, -
322, -341, and -342 airplanes; Model A340-200 series airplanes; and 
Model A340-300 series airplanes. The MCAI states:

    Fatigue damage has been found on the A330/A340 full scale 
fatigue test specimen in the FR40-to-fuselage skin panel junction. 
Corrective actions consisted of the following actions:

    --in-service installation of an internal reinforcing strap on 
related junction required by DGAC France AD 1999-448-126(B) and AD 
2001-070(B),
    --retrofit improvement of internal reinforcing strap fatigue 
life through recommended Airbus SB A330-53-3145, and
    --new design in production through Airbus modification 44360.

    Recently, during embodiment of a FR40 web repair on an A330 
aeroplane and during FR40 keel beam fitting replacement on an A340 
aeroplane, this internal strap was removed and rototest inspection 
was performed on several holes. Cracks were found on both left-hand 
(LH) and right-hand (RH) sides on internal strap, or butt strap, or 
keel beam fitting, or forward fitting FR40 flange.
    This condition, if not detected and corrected, could lead to 
crack propagation, possibly resulting in reduced structural 
integrity of the fuselage.
    For the reasons described above, this [EASA] AD requires 
repetitive High Frequency Eddy Current (HFEC) rototest inspections 
on the affected adjacent holes on both LH and RH sides between 
stringer 38 and 39 at the FR40-to-fuselage panel junction, and in 
case of crack finding, accomplishment of the associated corrective 
actions.
* * * * *

    You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0363.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI. We are 
issuing this AD because we evaluated all pertinent information and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of these same type designs.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, we 
find good cause that notice and opportunity for prior public comment 
are unnecessary. In addition, for the reason(s) stated above, we find 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2018-0363; Product 
Identifier 2017-NM-108-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, we provide the following cost estimates to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
             Action                  Labor cost        Parts cost                  Cost per product
----------------------------------------------------------------------------------------------------------------
Repetitive special detailed      54 work-hours x                 $0  $4,590 per inspection cycle.
 inspection.                      $85 per hour =
                                  $4,590 per
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
repair that would be required based on the results of the required 
actions:

[[Page 21860]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                      Labor cost              Parts cost              Cost per product
----------------------------------------------------------------------------------------------------------------
Repair.............................  9 work-hours x $85 per  Up to $3,200..........  Up to $3,965.
                                      hour = $765.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-09-11 Airbus: Amendment 39-19268; Docket No. FAA-2018-0363; 
Product Identifier 2017-NM-108-AD.

(a) Effective Date

    This AD becomes effective May 29, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
on which Airbus modification 44360 has not been embodied in 
production.
    (1) Airbus Model A330-301, -321, -322, -341, and -342 airplanes, 
all manufacturer serial numbers on which Airbus Service Bulletin 
A330-53-3093 has been embodied in service, except those on which 
Airbus Service Bulletin A330-53-3145 has been embodied in service.
    (2) Airbus Model A340-211, -212, -213 airplanes, all 
manufacturer serial numbers on which Airbus Service Bulletin A340-
53-4104 has been embodied in service.
    (3) Airbus Model A340-311, -312, and -313 airplanes, all 
manufacturer serial numbers on which Airbus Service Bulletin A340-
53-4104 has been embodied in service.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracks on both left-hand (LH) 
and right-hand (RH) sides on certain frame (FR) 40 locations. We are 
issuing this AD to detect and correct cracks of the fuselage panel 
junction fasteners at FR40 on both LH and RH sides. Such a condition 
could lead to crack propagation, possibly resulting in reduced 
structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Action(s)

    Within 30 days after the effective date of this AD, request 
instructions from the Manager, International Section, Transport 
Standards Branch, FAA, to address the unsafe condition specified in 
paragraph (e) of this AD; and accomplish the actions at the times 
specified in, and in accordance with, those instructions. Guidance 
can be found in Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) AD 2011-0171R1, dated 
January 11, 2013.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, International Section, Transport Standards Branch, 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the International Section, send it to the 
attention of the person identified in paragraph (i)(2) of this AD. 
Information may be emailed to: [email protected]faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office.

(i) Related Information

    (1) Refer to MCAI EASA AD 2011-0171R1, dated January 11, 2013, 
for related information. You may examine the MCAI on the internet at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0363.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax: 206-231-3229.

(j) Material Incorporated by Reference

    None.

    Issued in Des Moines, Washington, on April 27, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-09848 Filed 5-10-18; 8:45 am]
 BILLING CODE 4910-13-P
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